Method and System for Dispensing Gas Turbine Anticorrosive Protection

ABSTRACT

Methods and systems for dispersing an anticorrosion fluid to a turbine engine may be done while the turbine engine is online or offline. In an embodiment, a method may comprise selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid into an air duct fluidly connected with the turbine engine.

BACKGROUND OF THE INVENTION

A compressor of a gas turbine engine may be exposed to dust ingestionand entry of an occasional dislodged foreign object that bypasses theinlet and results in varying degree of impact damage (e.g., corrosion,tip erosion/rubs, trailing edge thinning and stator root erosion). A gasturbine engine also has blades and other structures of a turbine thatare subject over time to the buildup of deposits of various residuesthat are byproducts of the combustion process. Impact damage and depositbuild up results in loss of turbine efficiency and potential degradationof gas turbine engine components.

BRIEF DESCRIPTION OF THE INVENTION

Disclosed herein are methods and systems for dispensing turbine engineanticorrosive protection. In an embodiment, a system includes a sourceof an anticorrosion fluid for metal in fluid communication with an airduct and a turbine engine in fluid communication with the air duct,wherein the anticorrosion fluid is distributed to the turbine engine viathe air duct.

In an embodiment, a method includes selecting an anticorrosion fluid fora turbine engine and distributing the anticorrosion fluid into an airduct fluidly connected with the turbine engine.

In an embodiment, a system may include a processor adapted to executecomputer-readable instructions and a memory communicatively coupled tothe processor. The memory may have stored therein computer-readableinstructions that, if executed by the processor, cause the processor toperform operations including providing instructions to select ananticorrosion fluid for a turbine engine and providing instructions todistribute the anticorrosion fluid into an air duct fluidly connectedwith the turbine engine.

This Brief Description of the Invention is provided to introduce aselection of concepts in a simplified form that are further describedbelow in the Detailed Description. This Brief Description of theInvention is not intended to identify key features or essential featuresof the claimed subject matter, nor is it intended to be used to limitthe scope of the claimed subject matter. Furthermore, the claimedsubject matter is not limited to limitations that solve any or alldisadvantages noted in any part of this disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

A more detailed understanding may be had from the following description,given by way of example in conjunction with the accompanying drawingswherein:

FIG. 1 is a sectional view of a gas turbine engine including turbine andcompressor piping;

FIG. 2 is an exemplary illustration of a power plant system;

FIG. 3 illustrates a non-limiting, exemplary method of applying a gasturbine anticorrosive treatment;

FIG. 4 illustrates a non-limiting, exemplary method of applying a gasturbine anticorrosive treatment; and

FIG. 5 is an exemplary block diagram representing a general purposecomputer system in which aspects of the methods and systems disclosedherein or portions thereof may be incorporated.

DETAILED DESCRIPTION OF THE INVENTION

Disclosed herein are methods and systems for dispersing an anticorrosionfluid for a gas turbine engine, such as a polyamine based fluid. Apolyamine based fluid may be applied to a gas turbine engine by using anevaporative cooling system or an inlet fogging system. The polyaminebased fluid can be used for power augmentation, NOx abatement, or gridfrequency support, among other things. In an embodiment, appropriatelogic may be enabled to ensure that the polyamine based fluid cannot beused excessively to impart power augmentation, Nox abatement, or gridfrequency support, among other things. The application of the polyaminebased fluid may be based on one or more conditions such as environmentalconditions, rate of degradation, a gas turbine engine frame size, typeof fluid distribution performed, duration of fluid distribution, amongother things.

As used herein, the term “polyamine” is used to refer to an organiccompound having two or more primary amino groups —NH2. In an embodiment,an anticorrosion agent may comprise a volatile neutralizing amine whichneutralizes acidic contaminants and elevates the pH into an alkalinerange, and with which protective metal oxide coatings are particularlystable and adherent. Non-limiting examples of the anticorrosion agentinclude cycloheaxylamine, morpholine, monoethanolamine,N-9-Octadecenyl-1,3-propanediamine, 9-octadecen-1-amine, (Z)-1-5,dimethylaminepropylamine (DMPA), diethylaminoethanol (DEAE), and thelike, and a combination comprising at least one of the aforementioned.For example, anticorrosion fluid may include a combination of apolyamine (a multifunction organic amine corrosion inhibitor) andneutralizing amines (volatile organic amines). Different ratio blends ofthe anticorrosion fluid may be introduced by varying the valvealignment.

FIG. 1 is an exemplary illustration of a gas turbine engine 11 thatincludes cooling and sealing air valve and pipe components. Compressor15 may include a number of stages. As shown in FIG. 1, there may be anA-stage 54, a B-stage 55, or C-stage 56 of the compressor. The terms“A-stage”, “X-stage”, and the like are used herein as opposed to “firststage”, “second stage,” and the like so as to prevent an inference thatthe systems and methods described herein are in any way limited to usewith the actual first stage or the second stage of the compressor or theturbine. Any number of the stages may be used. Each stage includes anumber of circumferentially arranged rotating blades, such as blade 59,blade 60, and blade 61. Any number of blades may be used. The blades maybe mounted onto a rotor wheel 65. The rotor wheel 65 may be attached tothe power output drive shaft for rotation therewith. Each stage also mayinclude a number of circumferentially arranged stationary vanes 67. Anynumber of the vanes 67 may be used. The vanes 67 may be mounted withinan outer casing 70. The casing 70 may extend from a bellmouth 75 towardsturbine 17. The flow of air 22 enters the compressor 15 about thebellmouth 75 and is compressed through the blades (e.g., blade 59, 60,and 61, among others) and the vanes 67 of the stages before flowing tothe combustor.

FIG. 2 is an exemplary illustration of a power plant system 105. Innormal operation, inlet air flows into the inlet filter house 110 viathe inlet hoods 114, and through a plurality of filter elements. Thefiltered inlet air passes through a duct 112 (or similar passage) to agas turbine engine 116. Duct 112 may contain an evaporative coolingsystem 111. In another embodiment, an inlet fogger system may besimilarly situated at or near evaporative cooling system 111 in powerplant system 105. Evaporative cooling system 111 is generally usedsynonymously with an inlet fogger system, as discussed herein. Thetypical function of the evaporative cooling system 111 is to increasepower output from the engine by cooling the inlet air to the machine byvaporizing water. Gas turbine engine 116 includes a compressor section117, a combustion section 118, and a turbine section 119. High pressureair from compressor section 117 enters the combustion section 118 of thegas turbine engine 116 where the air is mixed with fuel and burned.

As illustrated in FIG. 2, evaporative cooling system 111 is fluidlyconnected with anticorrosion fluid piping 122. Anticorrosion fluidpiping 122 is fluidly connected with an anticorrosion fluid source 120.In an embodiment, an anticorrosion fluid may include a mixture of apolyamine based fluid and water. The water-polyamine mixture may be of apredetermined ratio and inserted into evaporative cooling system 111 viaanticorrosion fluid piping 122. The water-polyamine mixture may betransformed to a vapor (e.g., steam) or aerosolized (e.g., fog) via theevaporative cooling system 111. The polyamine based vapor may travelthrough duct 112 and into the compressor bellmouth. There may be anassortment of valves, mixing chambers, sensors, controls, or the like,as discussed and implied herein, that help determine whether to use thepolyamine based fluid and assist in the application of the polyaminebased fluid. The use of evaporative cooling system 111 to helpadminister an anticorrosion fluid may be done while the gas turbineengine is in online operation or during an online fluid distribution(e.g., online wash using a detergent or distributing an anticorrosionfluid).

In another embodiment, a source of anticorrosion fluid may be suppliedfrom an independent and external source, such as a tanker truck. Theexternal source can be manually connected via quick disconnectprovisions on anticorrosion fluid piping 122 fluidly connected with theevaporative cooling system 111. The evaporative cooling process asdiscussed herein may be used for dispersing of a saturated air streamgenerated from air in combination with a polyamine based fluid and watermixture, into the compressor. It is contemplated that a low-pressurefogger system may be used to deliver the anticorrosion fluid.

Anticorrosion fluid may be dispersed via evaporative cooling system 111when gas turbine engine 116 is offline or online. Gas turbine engine 116may be considered offline when the machine is operating at significantlybelow normal power generating output level. Whether gas turbine engine116 is online may be determined based on power output level, but usuallyincludes the gas turbine engine 116 operating at higher temperatures(e.g., turbine operating above 145° F.). During an offline distributiongas turbine engine 116 may be cooled down, until the interior volume andsurfaces have cooled down sufficiently (e.g., around 145° F.) so that awater or cleaning mixture being introduced into the gas turbine enginewill not thermally shock the internal metal and induce creep, or induceany mechanical or structural deformation of the material.

In an embodiment, just water and one or more anticorrosion agents may bemixed in a predetermined ratio. A water-anticorrosion agent mixture maybe held in a separate storage tank (e.g., a premixed anticorrosionfluid), The mixture for the resulting anticorrosion fluid may be basedon the gas turbine engine frame size, duration of distribution incombination with discharge, or flow requirement. The ratio also may beadjusted based on the type of amine.

Once mixed the anticorrosion fluid may be dispersed to create amolecular layer coating-a micro-coating on metal. Metal passivationimparts a protective shield to metal and/or metal alloy substrates fromenvironmental factors (e.g., high temperatures, combustion by-products,debris, etc.) exhibited in gas turbine engines by forming a coating(e.g., a metal oxide layer) which protects the metal or metal alloysubstrate from corrosive species. In an embodiment, the coating thatresults from the application of the anticorrosion fluid may serve tostrengthen the bonds in the metal or metal alloy substrate of acompressor, such as compressor 117. Based on the mixture of theanticorrosion fluid (e.g., type of anticorrosion agents), significantthermal decomposition of the anticorrosion coating may not be exhibiteduntil temperatures above 500° C. is reached. In an embodiment,successive anticorrosion treatment cycles may be applied to thecompressor 117 using the systems described herein, resulting in amulti-layer anticorrosion coating.

Anticorrosion fluid may impart corrosion resistance and/or inhibition tocompressor 117 by using metal passivation to provide an anticorrosioncoating on the metal and/or metal alloy substrates in a gas turbineengine with which the anticorrosion mixture comes into contact via theentry points at the evaporative cooling system 111, before compressor117, as discussed herein. Resultant anticorrosion fluid (partially orfully) coats stages of compressor 117 of gas turbine engine and variousmetallic components therein (e.g., compressor blades and stator vanes).

The anticorrosion fluid may comprise water and an anticorrosion agent ina particularly selected, predetermined ratio. Any anticorrosion agentthat is suitable to impart an anticorrosive coating in a gas turbineengine may be employed. In an embodiment, the anticorrosion agent is anorganic amine, which acts as a corrosion inhibitor by adsorbing at themetal/metal oxide surface of components in the gas turbine engine,thereby restricting the access of potentially corrosive species (e.g.,dissolved oxygen, carbonic acid, chloride/sulfate anions, etc.) to themetal or metal alloy substrate surface of the gas turbine enginecomponent. In an embodiment, the anticorrosion agent is two or moreorganic amines. In an embodiment, the anticorrosion inhibitor is apolyamine. In an embodiment, anticorrosion treatment may include acombination of polyamine and neutralizing amines.

Referring to FIG. 2, valving (not shown) connected with anticorrosionfluid piping 122 may enable selection between different sources ofanticorrosion agents or fluids based on application of the fluid to thecompressor 117. The anticorrosion fluid may be steam. Anticorrosionfluid may be supplied from an external source, e.g., a truck, and may bemanually connected via the quick disconnects as disclosed herein. Theanticorrosion fluid may be mixed automatically at a predetermined ratio(adjustable based on the type of amine) and dispersed thereafter. Inletand drain valves may be optimally positioned and aligned prior tointroduction of the anticorrosion fluid.

Power plant system 105 may incorporate a plurality of sensors (notshown) such as a motor sensor, a fluid level sensor, a fluid pressuresensor, a mixture outflow pressure sensor, a compressor pressure sensorwhich senses pressure in a compressor section of a gas turbine engine, aturbine pressure sensor which senses pressure in gas turbine engine 116,or valve position sensors, among other sensors. Power plant system 105may further include flow sensors configured to sense the rate of flow ofa fluid flowing (or not flowing) through piping.

FIG. 3 illustrates a non-limiting exemplary method 400 of applying ananticorrosion fluid to a gas turbine engine. In an embodiment, at step405, an anticorrosion fluid may be selected. The anticorrosion fluid maybe selected from known anticorrosion fluids for metals. At step 410, theanticorrosion fluid may be vaporized by an evaporative cooler. In analternative embodiment, at step 410, a fogger system or the like may fog(aerosolize) the anticorrosion fluid. At step 415, the anticorrosionfluid may be distributed to the gas turbine engine. Evaporative coolersand foggers are usually located in a duct between air intake filters anda compressor of the gas turbine engine. The flow of air in the ductassists in the distribution of the anticorrosion fluid to the compressorof the gas turbine engine.

FIG. 4 illustrates a non-limiting, exemplary method 500 of applying ananticorrosion fluid to a gas turbine engine. In an embodiment at step505, the condition of the gas turbine engine (e.g., compressor orturbine) may be determined. The condition may be determined based onsensors, borescope inspection, or the like. The condition may includewhether the compressor or turbine is clean and pretreated (e.g., amountof debris or dust), whether a gas turbine engine is in operation (e.g.,offline or online), how long the gas turbine engine has been inoperation, or turbine output, among other things. The condition ofwhether the gas turbine engine is clean may be determined by data fromfouling sensors, the elapsed time between cleanings, or atmosphericconditions during the operation of the gas turbine engine, among otherthings.

At step 510, the type of anticorrosion fluid to apply to the gas turbineengine may be determined based on the condition of the gas turbineengine. The condition of the gas turbine engine may include the type ofgas turbine engine, the amount of damage to the gas turbine engine, thetemperature of the gas turbine engine, the operating environment, thepower out level of the gas turbine engine, or the like. In anembodiment, the type of anticorrosion fluid to apply to the gas turbineengine may be determined based on a distribution point to the gasturbine engine. For example, the type of anticorrosion fluid may bechosen based on whether there is distribution via bellmouth nozzles nearthe bellmouth or via extraction ports (or other ports) near laterstages.

At step 515, an anticorrosion fluid may be applied to the gas turbineengine based on the condition of the gas turbine engine. If acompressor, turbine, or other gas turbine engine component is dirty whenan anticorrosion fluid is applied, the anticorrosion fluid may not bondproperly to the gas turbine engine components which in turn, may reducethe effectiveness of the applied anticorrosion fluid. In an embodiment,aerosolized anticorrosion fluid may be applied after cleaning of a gasturbine engine. The cleaning may include one or more of the following:the utilization of a detergent and demineralized water for compressorwashing; utilization of an “intra Rinse” solution or pre-passivatingtreatment followed by a neutralizing rinse.

Although an anticorrosion fluid, such as a polyamine based fluid, may besubstantially heat resistant, an anticorrosion fluid may becomeineffective at certain temperatures. Therefore it may be appropriate toapply the anticorrosion fluid at a particular stage of the gas turbinecomponent (e.g., compressor or turbine) or not at all based on thetemperature at the particular stage. The location of the application ofthe anticorrosion fluid may be controlled by valves (not shown) incommunication with a control system (e.g., control system 190), asdiscussed herein. The valves may be controlled automatically or manuallybased on a threshold condition (e.g., meeting a threshold temperature).

In an exemplary embodiment, control system 190 communicates, viawireless or hardwired, with the sensors described herein, and furthercommunicates with actuation mechanisms (not shown) provided to start,stop, or control the speed of motors. The control system may open,close, or regulate the position of valves used to accomplish theoperations of power plant system 105, as described herein.

Control system 190, as shown in FIG. 2, may be a computer system that iscommunicatively connected with a panel/display. Control system 190 mayexecute programs to control the operation of power plant system 105using sensor inputs and instructions from human operators via humanmachine interface (HMI) terminals. In addition, in an exemplaryembodiment, control system 190 may be programmed to alter (or restrict)the ratio of water to polyamine or other agent, alter (or restrict) thecycle times for distribution sequences, or alter (or restrict) the orderof steps in distribution or rinse cycles, or alter the order or restrictthe duration of the anticorrosion fluid dispensation.

Control system 190 is communicatively connected with power plant systemsand devices. Once all the predetermined logic permissive for theapplication of the anticorrosion fluid has been met, the onlinedistribution using the anticorrosion fluid may become active and theanticorrosion fluid may be appropriately applied. Control system 190 mayautomatically run the gas turbine engine based on apredetermined/predesigned sequence specifically designed foranticorrosion fluid operating mode. The method for online distributionsystem activation and operation includes determining that the poweroutput and other turbine control parameters have been satisfied foronline distribution. Control system 190 may attempt to maintain asubstantially constant air flow from the compressor to facilitatecontrolling a fuel to compressor discharge pressure ratio such that acombustor state does not lag changes in airflow during the distributionsequence. During operation this system will have the effect ofincreasing the “mass flow” through the turbine thereby permitting anincrease in power delivered to the grid. With the aforementioned inmind, control system 190 may be configured with the appropriate checksand limitations to ensure that it cannot be used excessively (e.g.,abused) for power augmentation, Nox abatement, or grid frequencysupport.

In an embodiment, during the application of the anticorrosion fluid(e.g., via bellmouth nozzles, via inlet fogging system, evaporativecooling system, etc.), control system 190 may be configured to provideinstructions to systems that help control gas turbine engine 116 tomaintain an appropriate power output level. An appropriate power levelmay be manually set, determined by analysis of the current or similargas turbine engines, or the like. In an embodiment, excessive use may beminimized by restrictive access to change online anticorrosion fluiddispersion control logic. For example, minimal access to change thepolyamine water ratio for online anticorrosion fluid dispersion, minimalaccess to change cycle time for anticorrosion fluid dispersion sequences(e.g., between dispersals), minimal access to change cycle time foronline anticorrosion fluid dispersion (e.g., during a dispersal), or thelike. Abuse of the online anticorrosion fluid dispersion or otherapplication of the anticorrosion fluid may be indicated by patterns inthe frequency and other data, as suggested herein, with regard to theapplication of the anticorrosion fluid.

Without in any way limiting the scope, interpretation, or application ofthe claims appearing herein, a technical effect disclosed herein is theutilization of a combination of chemicals (i.e., corrosion inhibitors)in a ratio of acid and alkaline chemicals in temperature supportiveenvironmental conditions to help the formation of a passivation layer onthe surface of the gas turbine engine compressor blades and statorvanes. The ratio may be predetermined. Corrosion mitigation may helpmaintain recovered performance for a longer duration. The application ofthe corrosion inhibitor may reduce the propensity for compressor bladeor turbine blade erosion from numerous water washes. Integrating theanticorrosion distribution system into the inlet fogging system,evaporative cooler, and other existing systems, as discussed herein, mayminimize a need for new extensive piping runs or casing penetrations.

FIG. 5 and the following discussion are intended to provide a briefgeneral description of a suitable computing environment in which themethods and systems disclosed herein and/or portions thereof may beimplemented. Although not required, portions of the methods and systemsdisclosed herein is described in the general context ofcomputer-executable instructions, such as program modules, beingexecuted by a computer, such as a client workstation, server, personalcomputer, or mobile computing device such as a smartphone. Generally,program modules include routines, programs, objects, components, datastructures and the like that perform particular tasks or implementparticular abstract data types. Moreover, it should be appreciated themethods and systems disclosed herein and/or portions thereof may bepracticed with other computer system configurations, including hand-helddevices, multi-processor systems, microprocessor-based or programmableconsumer electronics, network PCs, minicomputers, mainframe computersand the like. A processor may be implemented on a single-chip, multiplechips or multiple electrical components with different architectures.The methods and systems disclosed herein may also be practiced indistributed computing environments where tasks are performed by remoteprocessing devices that are linked through a communications network. Ina distributed computing environment, program modules may be located inboth local and remote memory storage devices.

FIG. 5 is a block diagram representing a general purpose computer systemin which aspects of the methods and systems disclosed herein and/orportions thereof may be incorporated. As shown, the exemplary generalpurpose computing system includes a computer 620 or the like, includinga processing unit 621, a system memory 622, and a system bus 623 thatcouples various system components including the system memory to theprocessing unit 621. The system bus 623 may be any of several types ofbus structures including a memory bus or memory controller, a peripheralbus, and a local bus using any of a variety of bus architectures. Thesystem memory includes read-only memory (ROM) 624 and random accessmemory (RAM) 625. A basic input/output system 626 (BIOS), containing thebasic routines that help to transfer information between elements withinthe computer 620, such as during start-up, is stored in ROM 624.

The computer 620 may further include a hard disk drive 627 for readingfrom and writing to a hard disk (not shown), a magnetic disk drive 628for reading from or writing to a removable magnetic disk 629, and anoptical disk drive 630 for reading from or writing to a removableoptical disk 631 such as a CD-ROM or other optical media. The hard diskdrive 627, magnetic disk drive 628, and optical disk drive 630 areconnected to the system bus 623 by a hard disk drive interface 632, amagnetic disk drive interface 633, and an optical drive interface 634,respectively. The drives and their associated computer-readable mediaprovide non-volatile storage of computer readable instructions, datastructures, program modules and other data for the computer 620. Asdescribed herein, computer-readable media is a tangible, physical, andconcrete article of manufacture and thus not a signal per se.

Although the exemplary environment described herein employs a hard disk,a removable magnetic disk 629, and a removable optical disk 631, itshould be appreciated that other types of computer readable media whichcan store data that is accessible by a computer may also be used in theexemplary operating environment. Such other types of media include, butare not limited to, a magnetic cassette, a flash memory card, a digitalvideo or versatile disk, a Bernoulli cartridge, a random access memory(RAM), a read-only memory (ROM), and the like.

A number of program modules may be stored on the hard disk, magneticdisk 629, optical disk 631, ROM 624 or RAM 625, including an operatingsystem 635, one or more application programs 636, other program modules637 and program data 638. A user may enter commands and information intothe computer 620 through input devices such as a keyboard 640 andpointing device 642. Other input devices (not shown) may include amicrophone, joystick, game pad, satellite disk, scanner, or the like.These and other input devices are often connected to the processing unit621 through a serial port interface 646 that is coupled to the systembus, but may be connected by other interfaces, such as a parallel port,game port, or universal serial bus (USB). A monitor 647 or other type ofdisplay device is also connected to the system bus 623 via an interface,such as a video adapter 648. In addition to the monitor 647, a computermay include other peripheral output devices (not shown), such asspeakers and printers. The exemplary system of FIG. 5 also includes ahost adapter 655, a Small Computer System Interface (SCSI) bus 656, andan external storage device 662 connected to the SCSI bus 656.

The computer 620 may operate in a networked environment using logicalconnections to one or more remote computers, such as a remote computer649. The remote computer 649 may be a personal computer, a server, arouter, a network PC, a peer device or other common network node, andmay include many or all of the elements described above relative to thecomputer 620, although only a memory storage device 650 has beenillustrated in FIG. 5. The logical connections depicted in FIG. 5include a local area network (LAN) 651 and a wide area network (WAN)652. Such networking environments are commonplace in offices,enterprise-wide computer networks, intranets, and the Internet.

When used in a LAN networking environment, the computer 620 is connectedto the LAN 651 through a network interface or adapter 653. When used ina WAN networking environment, the computer 620 may include a modem 654or other means for establishing communications over the wide areanetwork 652, such as the Internet. The modem 654, which may be internalor external, is connected to the system bus 623 via the serial portinterface 646. In a networked environment, program modules depictedrelative to the computer 620, or portions thereof, may be stored in theremote memory storage device. It will be appreciated that the networkconnections shown are exemplary and other means of establishing acommunications link between the computers may be used.

Computer 620 may include a variety of computer readable storage media.Computer readable storage media can be any available media that can beaccessed by computer 620 and includes both volatile and nonvolatilemedia, removable and non-removable media. By way of example, and notlimitation, computer readable media may comprise computer storage mediaand communication media. Computer storage media include both volatileand nonvolatile, removable and non-removable media implemented in anymethod or technology for storage of information such as computerreadable instructions, data structures, program modules or other data.Computer storage media include, but are not limited to, RAM, ROM,EEPROM, flash memory or other memory technology, CD-ROM, digitalversatile disks (DVD) or other optical disk storage, magnetic cassettes,magnetic tape, magnetic disk storage or other magnetic storage devices,or any other medium which can be used to store the desired informationand which can be accessed by computer 620. Combinations of any of theabove should also be included within the scope of computer readablemedia that may be used to store source code for implementing the methodsand systems described herein. Any combination of the features orelements disclosed herein may be used in one or more embodiments.

In describing embodiments of the subject matter of the presentdisclosure, as illustrated in the Figures, specific terminology isemployed for the sake of clarity. The claimed subject matter, however,is not intended to be limited to the specific terminology so selected,and it is to be understood that each specific element includes alltechnical equivalents that operate in a similar manner to accomplish asimilar purpose. An aerosolized polyamine based fluid, a vapor polyaminebased fluid, or a non-aerosolized liquid polyamine based fluid may beimplemented. Although a gas turbine for a power plant system isdiscussed, other similar turbine engine configurations are contemplatedherein. The anticorrosive treatment discussed herein may be appliedsimultaneously via different systems, such as an inlet bleed heatsystem, evaporative cooling system, fogger, bellmouth nozzle, extractionpiping, or other devices. Any combination of the features or elementsdisclosed herein with regard to a polyamine based fluid may be used inone or more embodiments.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they have structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

What is claimed:
 1. A system comprising: a source of an anticorrosionfluid comprising anticorrosion fluid for metal, the source in fluidcommunication with an air duct; and a turbine engine in fluidcommunication with the air duct, wherein the anticorrosion fluid isdistributed to the turbine engine via the air duct.
 2. The system ofclaim 1, wherein the anticorrosion fluid includes a polyamine basedfluid.
 3. The system of claim 1, further comprising: an evaporativecooler fluidly connected with the air duct, wherein the evaporativecooler transforms the anticorrosion fluid into a vapor.
 4. The system ofclaim 1, further comprising: a fogger system fluidly connected with theair duct, wherein the fogger system transforms the anticorrosion fluidinto an aerosol.
 5. The system of claim 1, wherein the anticorrosionfluid is in the form of a gas, a liquid, or an aerosol.
 6. The system ofclaim 1, further comprising: a valve fluidly connected with the sourceof the anticorrosion fluid; and a control system communicativelyconnected with the valve, wherein the control system adjusts the valvebased on a condition of the turbine engine received from at least one ofa borescope or fouling sensor.
 7. The system of claim 1, wherein theanticorrosion fluid is applied while the turbine engine is offline. 8.The system of claim 1, further comprising: a mixing chamber in fluidcommunication with the source of the anticorrosion fluid.
 9. The systemof claim 8, further comprising: a source of water in fluid communicationwith the mixing chamber, wherein the mixing chamber mixes ananticorrosion agent with the water to make the anticorrosion fluid,wherein the anticorrosion agent is selected based on a condition of theturbine engine.
 10. The system of claim 9, wherein the condition of theturbine engine comprises at least one of a power output level of theturbine engine, elapsed time between applying the anticorrosion fluid,elapsed operation time of the turbine engine, temperature of the turbineengine, or atmospheric conditions near the turbine engine duringoperation.
 11. The system of claim 1, wherein the anticorrosion fluidwas created from combining at least two of the following:cycloheaxylamine, morpholine, monoethanolamine,N-9-Octadecenyl-1,3-propanediamine, 9-octadecen-1-amine, (Z)-1-5,dimethylaminepropylamine (DMPA), diethylaminoethanol (DEAE), orpolyamine.
 12. A method comprising: selecting an anticorrosion fluid fora turbine engine; and distributing the anticorrosion fluid into an airduct fluidly connected with the turbine engine.
 13. The method of claim12, wherein the anticorrosion fluid includes a polyamine based fluid.14. The method of claim 12, further comprising: vaporizing theanticorrosion fluid using an evaporative cooler.
 15. The method of claim12, further comprising: aerosolizing the anticorrosion fluid using afogger.
 16. The method of claim 12, wherein the anticorrosion fluid wascreated from combining at least two of the following: cycloheaxylamine,morpholine, monoethanolamine, N-9-Octadecenyl-1,3-propanediamine,9-octadecen-1-amine, (Z)-1-5, dimethylaminepropylamine (DMPA),diethylaminoethanol (DEAE), or polyamine.
 17. The method of claim 12,further comprising: creating the anticorrosion fluid by mixing ananticorrosion agent with water at a set ratio based on a condition ofthe turbine engine.
 18. The method of claim 17, wherein the condition ofthe turbine engine comprises at least one of a power output level of theturbine engine, elapsed time between applying the anticorrosion fluid,elapsed operation time of the turbine engine, temperature of the turbineengine, or atmospheric conditions near the turbine engine duringoperation.
 19. A system comprising: a processor adapted to executecomputer-readable instructions; and a memory communicatively coupled tosaid processor, said memory having stored therein computer-readableinstructions that, if executed by the processor, cause the processor toperform operations comprising: providing instructions to select ananticorrosion fluid for a turbine engine; and providing instructions todistribute the anticorrosion fluid into an air duct fluidly connectedwith the turbine engine.
 20. The system of claim 19, wherein theanticorrosion fluid is distributed using at least one of an evaporativecooler or a fogger.